Patent Application
20110081234
The described subject matter relates generally to gas turbine engines and, more particularly, to an improved thermal expansion joint for a gas turbine engine.
Gas turbine engines have zones such as turbine sections which provide an elevated temperature working environment during engine operation. Engine components located in such an elevated working environment experience dramatic temperature changes between engine operation and non-operation conditions, resulting in thermal expansion and/or contraction. Due to different thermal expansion/contraction characteristics of engine components connected one to another, thermal expansion joints are widely used to allow thermal expansion/contraction of the connected components independently one from another in order to minimize thermal stress in the engine structures. Thermal expansion joints of various types are used in gas turbine engines. However, conventional thermal extention joints have some shortcomings. For example, restoration of contact faces of conventional thermal joints where fretting and wear marks are observed, is not convenient.
Accordingly, there is a need to provide an improved thermal expansion joint for gas turbine engines.
According to one aspect, the described subject matter provides a thermal expansion joint for a turbine engine, comprising a second engine component having generally radially-extending wall, the wall defining a slot; a first engine component disposed adjacent the second engine component and having at least one radially-extending surface adjacent the wall, the first and second components having differing thermal expansion coefficients; an insert extending into an axial passage defined in the radial surface of the first component, the insert aligned to be matingly received in the slot, the insert and slot respectively configured to allow for differential thermal radial expansion between the first and second components; and a removable fastener retaining the insert to the second component.
In accordance with another aspect, the described subject matter provides a method for joining an engine component to a radial wall of a stationary structure of a turbine engine, the method comprising providing the engine component, the component having an insert extending through an axial passage of the component and an axial hole extending from a first radial surface through the radial wall toward a second radial surface of the radial wall, thereby loosely restraining the component between the first radial surface of the radial wall and an enlarged head of the insert; and joining an end of the insert and the second radial surface of the radial wall together.
In accordance with a further aspect, the described subject matter provides an apparatus for joining components of a gas turbine engine while allowing thermal expansion/contraction thereof relative to each other, comprising a first component having opposed first and second surfaces and defining a hole extending through the first component between the opposed surfaces; a second component having at least one surface and defining a passage extending from the at least one surface through the component, the at least one surface abutting the first surface of the first component; an insert having opposed first and second ends, and an enlarged head integrated with the first end, the insert extending through the passage of the second component and snugly received in the hole, thereby loosely restraining the second component between the enlarged head of the insert and the first component to allow thermal expansion of respective components relative to each other in a direction substantially perpendicular to the passage of the second component; and a tack weld as a removable fastener joining the second end of the insert and the second surface of the first component together.
Further details of these and other aspects of the described subject matter will be apparent from the detailed description and drawings included below.
Reference is now made to the accompanying drawings depicting aspects of the described subject matter, in which:
Referring to
Referring to
An insert 50 is provided which has opposed ends 52, 54 with an enlarged head 56 integrated with the end 52. Optionally, the insert 50 is generally cylindrical, having a cylindrical stem 58 axially extending from the enlarged head 56 and a cylindrical end portion 60 extending axially from the stem 58 to form the end 54. The end portion 60 has a diameter less than the diameter of the stem 58.
It is optional to have the axial length of the stem 58 of the insert 50 less than the sum of the thicknesses of the radial wall 32 and the seal ring 40 and to have the hole 38 in the radial wall 32 configured accordingly. The seal ring 40 is loosely restrained between the enlarged head 56 of the insert 50 and the radial wall 32 such that thermal radial expansion of the respective radial wall 32 and the seal ring 40 relative to each other is allowed when the insert 50 extends through the slot 46 of the seal ring 40 and snugly received in the hole 38 of the radial wall 32. In this configuration, the slot 46 in the seal ring 40 has a width slightly greater than the diameter of the stem 58 of the insert 50.
The hole 38 may have an enlarged portion (not numbered) to receive a portion of the stem 58 of the insert 50. The enlarged portion of the hole 38 has a depth such that the insertion of the insert 50 into the hole 38 is limited to provide an axially gap (not numbered) between the radial wall 32 and the enlarged head 56 of the insert greater than the thickness of the seal ring 40. In use, a pressure differential across the seal ring 40 and the radial wall 32 presses the seal ring 40 against the radial wall 32 to maintain the abutment between the surface 34 of the radial wall 32 and the surface 44 of the seal ring 40. The radial dimension of the slot 46 is determined accordingly to allow adequate margin for thermal radial expansion/contraction of the seal ring 40 independent from the connected radial wall 32.
The hole 38 in the radial wall 32, or at least one axially section of the hole 38 may be sized to snugly receive an axially section of the insert 50. For example, the stem 58 of the insert 50 may be snugly received in the enlarged portion of the hole 38 and/or the end portion 60 of the insert 50 may be snugly received in the remaining portion of the hole 38.
The insert 50 is secured to the radial wall 32 by a tack weld 62 (see
The first and second components may have different thermal expansion coefficients and therefore may have different thermal expansion/contraction in response to the same temperature changes. The apparatus 30 is so configured as to allow the different thermal expansion/contraction of the first and second components.
According to this embodiment, tack weld 62 provides a removable fastener to the apparatus 30. When the insert 50 is to be removed from the engine for replacement or repairing during engine maintenance, the tack weld 62 may be removed by grinding, or other suitable removal technique. The tack weld 62 may be applied in only a desired circumferential location of the end portion 60 of the insert 50 for convenience of removing the tack weld 62 when desired in engine maintenance.
Alternately, any other suitable fastener apparatus may be employed. For example, as shown in
Optionally, the end portion 60 of the insert 50 projects axially out of the surface 36 of the radial wall 32. The tack weld 62 is therefore applied between the projecting section of the end portion 60 of the insert 50 and the radial surface 36 of the radial wall 32.
As an alternative to the cylindrical stem 58 of
In another example thermal expansion joint, shown in
The above description is meant to be exemplary only, and one skilled in the art will recognize that changes may be made to the embodiments described without departure from the scope of the described subject matter. For example, a seal ring attached to a mid-turbine frame is used exemplary for the embodiment described above, however, it is understood that the apparatus and the method described in this application is applicable for joining other components of a gas turbine engine while allowing thermal expansion/contraction thereof relative to each other. Although thermal expansion/contraction in radial direction is discussed in the above described embodiment, it is understood that the apparatus and method described above may also be applicable to allow thermal expansion/contraction in other directions which are substantially perpendicular to the passages of the components receiving the insert. Still, other modifications which fall within the scope of the described subject matter will be apparent to those skilled in the art, in light of a review of this disclosure, and such modifications are intended to fall within the appended claims.
